Aircraft propeller structure



July 25, 1961 R. K, ODOR 2,993,662

AIRCRAFT PROPELLER STRUCTURE Filed July '7',v 1958 INVENTOR, Aa/p/r Kl Odor 2,993,662 AIRCRAFT PROPELLER STRUCTURE Ralph K. Odor, Fisher Hills, Edmond, Okla. Filed July 7, 1958, Ser. No. 746,803 2 Claims. (Cl. 244-15) This invention relates to aircraft propeller structure and has for its object the improvement upon the propeller assembly for aircraft set forth in my US. Letters Patent No. 2,118,052, dated May 24, 1938, and to incorporate therein as a novel combination, the principles of US. Letters Patent No. 2,330,907, dated October 5, 1943 and relating to an aerodynamic device.

Accordingly, it is the primary object of the present invention to provide increased air flow through the tubular structure of said first-mentioned patent through use of relatively telescoped, frusto-conical, open end tubes in the nature of those depicted in Patent No. 2,330,907 by strategic positioning of such tubes forwardly of the propeller in coaxial relationship with the latter and with the tubular structure that receives the slip stream of such propeller.

In the drawing:

FIG. 1 is a plan view of an airplane incorporating the instant invention.

FIG. 2 is a fragmentary, front elevational view thereof; and

FIG. 3 is an enlarged, central, vertical, cross-sectional view through the tubular structure for receiving the slip stream and the coaxial tubes of the instant invention that are incorporated therewith.

Tubular structure for the airplane shown in FIGS. 1 and 2 which is best illustrated in FIG. 3 of the drawing, is essentially the same as that shown in said Patent No. 2,118,052; therefore, the principles thereof and manner of operation need not be repeated and such patent is incorporated herein by reference as may be necessary for a full and complete understanding of the improvements about to be described.

Essentially, it is to be noted that the tubular structure 10 is in the nature of an elongated, hollow body having a tubular leading section 12 and a semitubular trailing section 14, propeller 16 being disposed at the forwardmost end 18 of section 12.

It is to be noted that in order to render the improvements of the instant invention most effective, lower portion 20 of section 12 has been modified to present a longitudinal cross-section conforming with a preferred airfoil terminating in rather sharply defined feather edges, not only at the rearmost end of section 12 at 2.2, but in an edge 24 that is coincident with the forwardmost end 18 of section 12. In this same manner the upper portion 26 of section 12 has a longitudinal cross-section that is substantially the same as that of portion 20.

Additionally, through the medium of suitable support means 28, there is provided a plurality of coaxial, frustoconical, open-end tubes 30 and 32 of differing diameters forwardly of the end 18 of body 10. The size, number, configuration, relative disposition and operation of the tubes 30 and 32 illustrated in the drawing, may be much the same as disclosed in said Patent No. 2,330,907 and, therefore, the teachings of such patent setting forth the 2,993,662 Patented July 25, 1961 advantages of the tubular structure 30 and 3-2 in an air stream need not be repeated.

It is important to note however, that tubes 30 and 32 are disposed forwardly of the propeller 16 so as to increase the flow of air through the body 10 and that such tubes 30-32 are preferably aligned axially with propeller 16 and with the body 10. Manifestly, tubes 30 and 32 are spaced apart in partial telescoping relationship as is clear in FIG. 3, and the smaller ends of both tubes face propeller 16. The end 18 of body 10 has a diameter that is greater than the maximum diameter of tube 32 and, of course, the maximum diameter of the latter is appreciably greater than that of the tube 30. Consequently, the tubular structure 3032 progressively increases in diameter as the open end 18 of the body section 12 is approached.

It has been found that the combined effects of the tubular structure 10 of Patent No. 2,118,052, as modified in the airfoils 20 and 26, coupled with high speed propeller 16 and the tubular construction 3032 of Patent No. 2,330,907, provide additional thrust and lift in connection with aircraft and in some instances, tests have revealed as much as 20% advantage.

Having thus described the invention what is claimed as new and desired to be secured by Letters Patent is:

1. In aircraft propeller structure, the combination of a hollow body having a tubular leading section and a semitubular trailing section; a propeller; means mounting the propeller for rotation in the plane of the forwardmost end of said leading section; and a plurality of coaxial, frusto-conical, open end tubes disposed forwardly of said propeller and axially aligned with the latter and with said body, said tubes being arranged in spaced, partially telescoping relationship, said forwardmost end having a diameter greater than the diameter of the smaller outlet end of the innermost tube.

2. In aircraft propeller structure, the combination of a hollow body having a tubular leading section and a semi-tubular trailing section; a propeller; means mounting the propeller for rotation in the plane of the forwardmost end of said leading section; and a plurality of coaxial, frusto-conical, open end tubes disposed forwardly of said propeller and axially aligned with the latter and with said body, said tubes being arranged in spaced, partially telescoping relationship with the smaller outlet ends thereof facing said propeller; and support means on said leading section projecting forwardly from said forwardmost end of the latter and rigidly secured to said tubes for axially mounting the latter with the smaller outlet ends spaced from said propeller and said forwardmost end, the latter having a diameter greater than the diameter of the smaller outlet end of the innermost tube.

References Cited in the file of this patent UNITED STATES PATENTS 344,000 Magee June 22, 1886 2,118,052 Odor May 24, 1938 2,330,907 Odor et al. Oct. 5, 1943 FOREIGN PATENTS 389,288 Great Britain Mar. 16, 1933 473,377 Germany Mar. 14, 1929 763,758 Germany Feb. 19, 1934 

